(19)
(11) EP 0 971 095 A3

(12) EUROPEAN PATENT APPLICATION

(88) Date of publication A3:
20.12.2000 Bulletin 2000/51

(43) Date of publication A2:
12.01.2000 Bulletin 2000/02

(21) Application number: 99305036.8

(22) Date of filing: 25.06.1999
(51) International Patent Classification (IPC)7: F01D 5/18
(84) Designated Contracting States:
AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE
Designated Extension States:
AL LT LV MK RO SI

(30) Priority: 06.07.1998 US 110532

(71) Applicant: UNITED TECHNOLOGIES CORPORATION
Hartford, CT 06101 (US)

(72) Inventor:
  • LaFleur, Ronald Samuel
    Potsdam, New York 13676 (US)

(74) Representative: Leckey, David Herbert 
Frank B. Dehn & Co., European Patent Attorneys, 179 Queen Victoria Street
London EC4V 4EL
London EC4V 4EL (GB)

   


(54) A coolable airfoil for a gas turbine engine


(57) A hollow airfoil 12 is provided having a leading edge 18, a trailing edge 20, and a wall 22 including a suction side portion 24 and a pressure side portion 26. The wall 22, which includes an interior surface 40 and an exterior surface 42, surrounds a first cavity 30 and a second cavity 32, separated from one another by a rib 34 extending between the suction side and pressure side wall portions. The first cavity 30 is contiguous with the leading edge 18. The airfoil 12 further includes a coolant flow splitter 44 attached to the wall interior surface 40 within the first cavity 30, and at least one metering orifice 50 disposed in the rib 34. The metering orifice(s) 50 are substantially aligned with the coolant flow splitter 44, such that cooling air passing through the metering orifice(s) 50 encounters the flow splitter 44. The flow splitter 44 splits the cooling air flow and directs it along the wall interior surface 40.






Search report